Attachment for aeroplanes.



D. F. CASHMAN & C. 'A. BROWNFIELD.

ATTACHMENT FQRAEROPLANES.

APPLICATION FILED 'APR. 14, 1914.

Patentd July 4, 1916.

D. F. CASHMAN & C. AW'BROWNFIELD.

ATTACHMENT FOR AEROPLANES.

APPLICATION FILED APR. 14, 19x4.

Patented July 4, 1916.

5 SHEETS-SHEET 2 I Ti:

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wn ield D. F. CASHMAN & C. A. BROWNFIELDQ ATTACHMENT FOR AEROPLANES.APPLICATION HLED APR.1'4, 1-91 4.

Patented July 4, 1916.

5 SHEETS-SHEET 3- 2 ield 11E Gas/am an U, Br0wn D. F. CASHMAN & C- ABROWNFIELD.

ATTACHMENT FOR AEROPLANES.

, APPL|CAT|0N FILED APR. I4, 1914- 1,190,248. Patented July 4, 1916.

5 SHEETS-SHEET 4.

DENIS F. CASHMAN AND CHRIST A. BROWN'FIELD, 0F ZANESVILLE, OHIO.

ATTACHMENT FOR AEROPLANES.

Specification of Letters Patent.

Patented July 4, 1916.

Application filed April 14, 1914. Serial No. 831,858.

have invented certain new anduseful Improvements in Attachments forAeroplanes; and we do hereby declare the following to be a full, clear,and exact description ofthe invention, such as will enable othersskilled in the art to which it appertains to make and use the same.

0111 invention relates to improvements in aeroplanes of that typewherein the wings are mounted for independent pivotal movements onhorizontal axes extending laterally in the same plane from oppositesides of the fuselage.

One object of theinvention is the provision of novel means operable bythe wings to automatically and proportionally increase the angle ofincidence of one wing as the angle of incidence of the other wing isdecreased, whereby to maintain a lateral balance or equilibrium of theaeroplane.

A further object of the invention is the provision of manually operablemeans by which the angle of incidence of one wing may be increased andthe angle of incidence of the other decreased to effect a lateralbalance or equilibrium of the aeroplane.

A still further object of the invention is the provision of manuallyoperable means by which the angle of incidence of both wings may besimultaneously increased for" starting, alighting, or slow flying, orsimultaneously decreased for fast flying.

A still further object of the invention is the provision of reliable andeflicient means for bracing the wings of the aeroplane independently,one of the other, without connecting the braces directly to the fuselageor frame of the machine.

' With the above and other objects in view,

the invention consists in the construction,

'- combination and arrangement of parts hereinafter fully described,claimed, and illustrated in, the accompanying drawings, wherein:

Figure 1 is a front elevation of an aeroplane constructed in accordancewith our invention, the automatic means and :the

manually operable means by which a lateral I balance or equilibrium ofthe aeroplane may be maintained being shown diagrammatically, Fig. 2 isa top plan view with. one wlng broken away, showing vdlagrammaticallythe manually operablemeans by which a lateral balance or equilibrium ofthe aeroplane may be maintained, Fig. 3 is a top plan view of theaeroplane, showing diagrammatically the automatic means by which alateral balance or equilibrium of the aeroplane is maintained, Fig. 4 isa detail side elevation of one of the wings, illus- .'trating the mannerof bracing the same,

Fig. 5 is a side elevation of a modified form of the invention appliedto a biplane, Fig. 6 is a detail view in elevation of the manuallyoperable means by which a lateral bal-' ance or equilibrium of theaeroplane may be maintained, Fig. 7 is a detail view of the upper end ofone of the struts, Fig. 8 is a view in side elevation of the means bywhich the angle of incidence of both wings may be simultaneouslyincreased or decreased, Fig. 9 is-a sectional view taken on the planeindicated by the line 9-9 of Fig. 8, and Fig. 1.0 is a perspective view.illustrating the automatic and the manually operable means formaintaining a lateral balance or equi-- Referring to the drawings byreferencenumerals, 1 designates the landing frame of an aeroplaneconstructed in accordance with our invention. A .The landing frame maybeof the usual .or any suitable construction. Journaled upon thelandingframe 1 are ground wheels 2 and mounted thereon is the fuselage3. The, wings 4 are independently pivoted upon' the fuselage. 3, eachbeing secured to a shaft or tube 5 of steel. The tubes or shafts 5extend through the wings 4 near the dips 6 of the front edges of thewings. The tubes or shafts 5 extend inwardly beyond the inner side edgesof the wings 4 and the inner ends of the tubes or shafts are journaledin ball bear- D STATESPATENT OFFICE.

ings 7 carried. by the fuselage 3. Struts 8 are secured to the innerends of the tubes or v shafts 5 and extend above and below the wings 4.Braces 9 ofsteel wire are secured at their lower ends to the upper sidesof the'wings 4 and at their upper ends to the upper ends of the struts8. Braces 9 also of steel wire are secured at their upper ends to theundersides of the wings 4 and at their lower ends to the lower endsofthe connected at a the struts 8 are provided with rings 10 and 10,respectively, to'which the upper and lower ends of the braces 9 and 9are secured, respectively.

The wings 4 and struts 8 are rigidly secured to the shafts 5, and theshafts 5 are adapted to rotate in the bearings 7. It will thus be seenthat the wings 4 are mounted for independent pivotal movement onhorizontal axes extending laterally in the same plane for opposite sidesof'the fuselage 3. As shown diagrammatically in Fig. 3 of the drawings,the wings 4 are connected by means which is operable by the wings toautomatically and proportionably increase the angle of incidence of onewing as the angle of incidence of the other wingis decreased, whereby tomaintain an automatic lateral balance or equilibrium of the aeroplane.This means comprises a wire cable 1.1 which passes around a pulley 12 atthe front of the fuselage 3 and around a pulley 13 at the rear of thefuselage, and which is point between the pulleys to the lower ends ofthe struts 8. When the angle of incidence of one of the wings 4 isreduced, the lower end of the strut of that wing is moved rearwardly.Such a movement of the lower end of'this strut 8 pulls the cable 11 in adirection to move the lower end of the other strut forwardly, and such amovement of the lower end of the other strut increases the angle ofincidence of the wing carried by that strut. It will thus be apparentthat if the angle of incidence of one wing is reduced, the angle ofincidence of the other wing will be automatically and proportionablyincreased, and that a lateral balance or equilibrium of the aeroplanewill be maintained. By reference to Figs. 8 and 10 of the drawings, itwill be seen that the pulley 12 is journaled upon a block 14 which iscarried by a rod 15. The rod 15 is slidably mounted at the front of thefuselage 3 in the members 16 and 16. A grooved disk 17 is mounted uponthe rod 15 in advance of the forward member 16*, and it is'held in placeby a nut 17" and a lock nut 17 spring 18 surrounds-the rod 15 and islocated between the grooved disk 17 and the forward member 16*. Thepulley 13 is journaled upon a block 18* which is carried by a rod 19.The rod 19 is slidably mounted upon a rear member 20 of the fuselage 3.Surrounding the rod 19 and located between the member 20 and a pin 21,is a'contractile' spring 22.

By reference to Figs. 2, 6 and 10 of the drawings, it will be seen thatthere is provided means by which the angle of incidence of one of thewings may be increased and the angle of incidence of the other decreasedmanually to effect the lateral balance or equilibrium of theaeroplane.This means comprises a lever 22 which is fulcrumed at a pointintermediate its ends, as at 23, upon the fuselage 3 at a point adjacentthe operators seat 24. A sector rack 25 and a dog 26 are provided topermit the lever 22 to be secured against accidental movement from itsadjusted osition. This means also comprises cables 2 and 28. The cable27 is secured as at 29 to the lever 22 at a point above its fulcrum 23,and the cable 28 is secured to the lever as at 30 at a point below itsfulcrum. The cable 27 passes from the lever 22 around a pulley 31journaled upon the block 14 to the lower end of one of the struts 8, andis suitably attached to the strut. The cable 28 extends from the lever22 around the pulley 32 to the lower end of the other strut 8.. Thecable 28 is attached in any suitable manner to this strut, and thepulley 32 is journaled upon the block 14. As the cables 27 and 28 aresecured to the lever 22 at points above and below the fulcrum,respectively, the

movement of the lever 22 in a forward direction will slack the cable 27and exert a rearward pull upon the cable 28, resulting in an increase inthe angle of incidence of the wing 4 to which the cable 27 is attachedand a decrease in the angle of incidence of the wing 4 to which thecable 28 is attached. The rearward movement of the lever 22 will slackthe cable 28 and exert a rearward pull upon the cable 27 resulting in anincrease in the angle of incidence of the wing 4 to. which the cable 28is attached and a decrease in the angle of incidence of the wing 4 towhich the cable 27 is attached.

In Figs. 8 and 10 of the drawings is illustrated the manually operablemeans by which the angle of incidence of both wings may besimultaneously increased for starting, alighting or slow flying, orsimultaneously decreased for fast flying. This means comprises the footoperated lever 33 which is fulcrumed at a point between its ends, as at34, to the fuselage in advance of the pilots seat 24. A cable 35 issecured at its rear end to the lower end of the lever 33 and at itsfront end to the lower end of a lever 36.

The lever 36 is fulcrumed at a point between its ends, as at 37, to theforward end of a bar 38 secured to the front of the fuselage 3. Theupper end of the lever 36 is forked as at 39. The forked end of thelever 36 fits in the groove of the disk 17. When a pressure acting in adownward and forward direction is applied to the foot plate 40 of thelever 33, the rod 15 and pulley block 14 are moved forwardly. Thismovement of the block 14 exerts a forward pull upon the cable 11, movingthe lower end of the struts 8 forwardly. This movement of the lower endsof the struts 8 causes. the angle of incidence of both wings 4 to beoted, at 42, to the lever and which is provided with a foot plate 43.The lower end of the dog is adapted to be moved into and a out ofengagement with the teeth of a ratchet plate 44. During the adjustmentof the wings 4 by the foot pedal 33, the spring 22 and the spring 18 aretensioned, and in V view thereof the Wings 4 are returned to theiroriginal positions as soon as the dog 41 is moved out of engagement withthe ratchet 44 by the springs.

It should be apparent from the foregoing description, taken inconnection with the accompanying drawings that we provide an aeroplane,the lateral balance or equilib ium of which is maintained automatically.It

should also be apparent that the lateral balance or equilibrium of theaeroplane may be maintained manually, and that the angle of incidence ofboth wings may be simultaneously increased for starting or alighting orslow flying, or simultaneously increased for fast flying, by .means ofthe foot lever 33.

As shown in Fig. 5 the strut S ris mounted centrally upon the axle a ofa biplane. The upper wing b and the lower wing 12 and the lower wing 0are connected to strut 8 at d and the vertical brace c connects the twowlngs.

The wing braces, not shown, extend from the opposite ends of the strut 8to the wings, and said strut is provided with rings 8 for the-connectionof thebraces similar to those shown in Fig. 7 of the drawings.

Certain modifications and changes may be made in the details ofconstruction without departing from the spirit and scope of theinvention as defined in the claims.

Having thus fully described our invention, what we claim and desire tosecure by Letters Patent is:

1. An aeroplane including a frame, shafts journaled on the frame, wings.carried by the shafts, struts carried by the shafts and extending belowthe wings, a spring supported pulley located at the front of the frame,a spring supported pulley located at the rear of the frame, and a cablepassing about said pulleys, said cable being secured at pointsintermediate the pulleys to the lower ends of said struts.

2. An aeroplane including a frame, shafts journaled on the frame, wingscarried by the shaft, struts carried by the shafts and projectingfbelowthe wings, a pulley journaled at the front of the frame, another pulleyjournaled at the rear of the frame, a cable passing about said pulleys,said cable being secured at points intermediate the pulleys to the lowerends of said struts,

other pulleys journaled at the front of the frame, a lever pivoted tothe frame at a point in the rear of said front pulleys, other cablessecured to the lower ends of said struts and passing about said otherfront pulleys, one of said other cables being secured to the lever at apoint above its pivot and the other to the lever at apoint below itspivot.

3. An aeroplane including a frame, shafts journaled on the frame, wingscarried by the shafts, struts carried by the shafts and extending belowthe wings, a spring supported pulley block located at the front of themachine, a spring supported pulley block located at the rear of theframe, a pulley journaled on each of said blocks, a cable passing aboutthe pulleys, said cable being secured at a point intermediate thepulleys to the lower ends of the struts, other pulleys journaled on saidfront pulley block, other cables secured to the lower ends of saidstruts and passing around said other pulleys, a lever pivoted to theframe, said other cables having their ends connected to 1 the lever at'apoint above and below the pivot respectively, and means by which saidfront pulley block can be manually moved.

4. An aeroplane including a frame, shafts journaled on the frame, wingscarried by the shafts, struts carried by the shafts and extending belowthe wings, a spring supported pulley block located at the front-of theframe, a spring supported. pulley block located at the rear of theframe, a pulley journaled on each of said blocks, a cable passing aboutthe pulleys, said cable being secured at a point intermediate thepulleys to the lower ends of the struts, other pulleys journaled on saidfront pulley block, other cables secured to the lower ends of saidstruts and passing around said other pulleys, a lever pivoted to theframe, said other cables having their ends connected to the the angle ofincidence of both wings may be simultaneously increased or decreased,and a second means connecting the lower ends of said struts, said secondmeans being adapted to be operated independently of the first means bywind pressureand on the increase of the angle of incidence of one wingto automatically and proportionally reduce the angle of incidence of theother wing.

I 6. An aeroplane'including a frame, shafts journaled on said frame,wings carried by the shafts, struts carried by the shafts and extendingbelow the wings, means connected to the lower ends of said struts bymeans of which the angle of incidence of one wing may be increased andthe. angle of incidence of the other wing decreased manually, and asecond means connecting the lower ends of said struts, said second meansbeing adapted to be operated independently of the first means by windpressure and on the increase of the angle of incidence of one wing e toautomatically and proportionally reduce the angle of incidence of theother wing. 7 An aeroplane including a frame, shafts journaled on saidframe, wings carried by the shafts, struts carried by the shafts andextending below thewings, means connected to the lower ends of thestruts so that the angle of incidence of one wing may be increased andthe angle of incidence of the other wing decreased manually, a secondmeans by which the angle or angles of incidence of the wings may beincreased or decreased manually and simultaneously, and a'third meansconnecting the lower ends of said struts, said third means being adaptedto be operated independently of the first and second meansby and on thereductionof the angle of incidence of one wing to automati- 4 cally andproportionally increase the angle of incidence of the other wing.

In testimony whereof we afiix our signatures in presence of twowitnesses.

' DENIS F. CASHMAN.

CHRIST A. BROWNFIELD. Witnesses:

GEORGE BROWN, CALDWELL A. BROWN.

